Matching response of a blade path temperature limit signal to characteristics of a gas turbine

ABSTRACT

In a primary or backup control system for operating a gas turbine, a blade path temperature limit signal is generated which acts as a check on a fuel scheduling signal to the turbine which might otherwise cause excursion of the blade path temperature beyond prescribed limits. The means for generating the blade path temperature limit signal is adapted however so that a preliminary error signal is conditioned to behave in one manner in response to a condition of increasing temperature and in another manner to a condition of decreasing temperature. 
     This two-way response is achieved by utilizing a plurality of proportional signal limiters, each one of which is matched to or tuned in accordance with the characteristics of the gas turbine. Further, the response duality is automatic and subject to the particular condition of temperature change which obtains. 
     In addition, means are provided for generating a temperature limit signal which is clamped to a fixed, predetermined percentage of the fuel scheduling signal. This signal is employed, under appropriate conditions, in place of the conditioned error signal to insure that the conditioned error signal does not otherwise set the fuel scheduling signal at less than the fixed percentage above its 100% value. Acting in concert, the means for conditioning the preliminary error signal and the means for generating the clamped temperature signal yield increased turbine protection, greater operating stability and more rapid control response where permissible.

CROSS-REFERENCE TO RELATED APPLICATIONS

Reference is hereby made to the following copending and related applications, all of which are assigned to the present assignee:

U.S. patent application Ser. No. 476,182 filed on June 4, 1974, now U.S. Pat. No. 3,975,902 in the names of Smith et al, entitled "Local Maintenance Controller For Gas Turbine Power Plants Having a Primary Control System", which application is incorporated herein by reference;

U.S. patent application Ser. No. 82,470 filed on Oct. 20, 1970 in the names of J. Reuther and T. Giras, entitled "System And Method For Operating Industrial Gas Turbine Apparatus And Gas Turbine Electric Power Plants Preferably With A Digital Computer Control System", now abandoned in favor of U.S. patent application Ser. No. 319,114, filed on Dec. 29, 1972 as a streamline continuation thereof, now abandoned;

U.S. patent application Ser. No. 82,469 filed on Oct. 20, 1970 in the names of R. Kiscaden and R. Yannone, entitled "System And Method For Accelerating And Sequencing Industrial Gas Turbine Apparatus And Gas Turbine Electric Power Plants Preferably With A Digital Computer Control System", now abandoned in favor of U.S. patent application Ser. No. 252,948, filed on May 12, 1972 as a streamline continuation thereof, and U.S. patent application Ser. No. 252,131, filed on May 10, 1972 as a divisional of the originally filed, above-mentioned, U.S. patent application Ser. No. 82,469;

U.S. patent application Ser. No. 82,467 filed on Oct. 20, 1970 in the name of T. Reed, entitled "Improved System And Method For Operating Industrial Turbine Apparatus And Gas Turbine Electric Power Plants Preferably With A Digital Computer Control System " now abandoned;

U.S. patent application Ser. No. 99,491 filed on Dec. 18, 1970 in the name of J. Reuther, entitled "System And Method Employing A Digital Computer For Automatically Synchronizing A Gas Turbine Or Other Electric Power Plant Generator With A Power System", now abandoned in favor of U.S. patent application Ser. No. 276,508, filed on July 31, 1972 as a streamline continuation thereof;

U.S. patent application Ser. No. 99,493 filed on Dec. 18, 1970 in the name of T. Reed, entitled "System And Method Employing A Digital Computer With Improved Programmed Operation For Automatically Synchronizing A Gas Turbine Or Other Electric Power Plant Generator With A Power System", now abandoned in favor of U.S. patent application Ser, No. 276,343, filed on July 31, 1972 as a streamline continuation thereof;

U.S. patent application Ser. No. 205,261 filed on Dec. 6, 1971 in the names of R. Yannone and R. Kiscaden, entitled "Improved Control System And Method For Controlling Dual Fuel Operation Of Industrial Gas Turbine Power Plants Preferably Employing A Digital Computer", now abandoned in favor of U.S. patent application Ser. No. 310,520, filed on Nov. 29, 1972 as a streamline continuation thereof, now U.S. Pat. No. 3,866,108;

U.S. patent application Ser. No. 205,263 filed on Dec. 6, 1971 in the name of J. Reuther, entitled "Industrial Gas Turbine Power Plant Control System Having Capability For Effecting Automatic Fuel Transfer Under Load Preferably Employing A Digital Computer", now abandoned in favor of U.S. patent application Ser. No. 308,892, filed on Nov. 22, 1972 as a streamline continuation thereof, now U.S. Pat. No. 3,919,623;

U.S. patent application Ser. No. 155,905 filed on June 23, 1971 in the names of R. Yannone and T. Reed, entitled "Improved System And Method For Monitoring And Controlling Operation of Industrial Gas Turbine Apparatus And Gas Turbine Electric Power Plants Preferably With A Digital Computer Control System", now abandoned in favor of U.S. patent application Ser. No. 317,839, filed on Dec. 26, 1972 as a streamline continuation thereof;

U.S. patent application Ser. No. 189,632 filed on Oct. 15, 1971 in the names of R. Yannone and R. Kiscaden, entitled "Improved Digital Computer Control System And Method For Monitoring And Controlling Operation Of Industrial Gas Turbine Apparatus To Drive Simultaneously An Electric Power Plant Generator And Provide Exhaust Gases To An Industrial Process", now abandoned in favor of U.S. patent application Ser. No. 323,593, filed on Jan. 15, 1973 as a streamline continuation thereof now U.S. Pat. No. 3,891,915;

U.S. patent application Ser. No. 189,633 filed on Oct. 15, 1971 in the names of J. Reuther and T. Reed, entitled "Improved Digital Computer Control System And Method For Monitoring And Controlling Operation of Industrial Gas Turbine Apparatus Employing Expanded Parameteric Control Algorithm", now abandoned in favor of U.S. patent application Ser. No. 326,718, filed on Jan. 26, 1973 as a streamline continuation thereof, now U.S. Pat. No. 3,866,109; and

U.S. patent application Ser. No. 204,944 filed on Dec. 6, 1971 in the name of G. Rankin, entitled "Industrial Gas Turbine Power Plant Control System And Method For Implementing Improved Dual Fuel Scheduling Algorithm Permitting Automatic Fuel Transfer Under Load", now abandoned in favor of U.S. patent application Ser. No. 332,457, filed on Feb. 14, 1973, as a streamline continuation thereof now U.S. Pat. No. 3,875,380.

Reference is also made to the following related, copending and commonly filed and assigned applications, all of which are hereby incorporated by reference:

U.S. patent application Ser. No. 551,201 filed in the names of Leonard H. Burrows, entitled "Delayed Ramping In The Primary Control System Or Local Maintenance Controller Of A Gas Turbine Implemented Electrical Power Plant";

U.S. patent application Ser. No. 551,204 filed in the names of Jack R. Smith and Leonard H. Burrows, entitled "Time Delayed Relay Sequencer and Alarm Reset for a Gas Turbine Local Maintenance Controller";

U.S. patent application Ser. No. 551,203, now US. Pat. No. 3,978,659 filed in the name of Richard S. Heiser, entitled "Bumpless Transfer in Shifting Control Command Between the Primary and Backup Control Systems of a Gas Turbine Power Plant".

BACKGROUND OF THE INVENTION

The present invention relates to the control of a gas turbine or gas turbine power plane and, more particularly, to means for conditioning the generation of a blade path temperature limit signal to reflect the characteristics of the gas turbine. The present invention is equally suitable for employment in a primary control system of a gas turbine or plant or in a local maintenance or backup controller therefor.

In the local maintenance controller described in the above-referenced U.S. patent application Ser. No. 476,182, or in the primary control system for a gas turbine implemented power plant described in the above-referenced U.S. patent application Ser. No. 82,470, the particular signal generated to control fuel flow to the turbine, for purposes of varying speed or acceleration, is limited, inter alia, by a blade path temperature signal. In other words, a continued or increased flow of fuel, however otherwise correct, will be reduced if such continuation or increase will have or has the effect of raising blade path temperature above a prescribed limit. On the other hand, where blade path temperature is safely below such a limit, fuel flow could be increased above the quantity called for by the control system.

Unfortunately, as blade path temperature rises in response to increased fuel flow, the temperature increase and therefore the flow of fuel must be limited to a relatively slow rate so that the prescribed limit is not exceeded, i.e. can be safely approached without overshoot. Conversely, when cutting back on fuel flow and dropping away from the prescribed limit, the rate of reduced fuel flow can be relatively high, i.e., can be rapidly reduced.

As is apparent, the rate at which the signal regulating fuel flow can be changed, reflects a compromise between slow rate increases and fast rate decreases. In the case of the control system described in the aforementioned U.S. patent application Ser. No. 476,182, for example, the effects of reducing fuel flow where permissible are limited only by the inertial characteristics of the turbine whereas in increasing fuel flow, the limiting factor is the permissible growth rate of the control signal output or fuel scheduling signal.

However, in order to insure that any selective variation of the effects of the blade path temperature limit signal are not adverse, means for limiting excursions in the temperature limit signal to a predetermined level would be needed.

Consequently, there exists a specific need to provide a means of selectively varying the effect of a blade path temperature limit signal depending on whether overall control is proceeding away from or towards such limit consistent with the foregoing.

SUMMARY OF THE INVENTION

Accordingly, there is provided, in conjunction with a gas turbine control system, a means for generating a blade path temperature error signal in matched response to the direction in which overall control is proceeding with respect to the temperature limit. Specifically, the means for generating the blade path temperature error signal is adapted so that a preliminary error signal is increased at a first rate when the temperature limit is approached and at a second rate when control action dictates a departure therefrom. Moreover, the variation in the error signal is matched to performance characteristics and is automatic in operation.

In the present invention, this result is achieved by setting the proportional section of a proportional high signal limiter to the first rate of change desired and by doing likewise to a second, low signal limiter. With the outputs of both limiters connected to a proportional plus integral controller, the rate of integration becomes a function of the selected rate of whichever limiter is active thereby matching the response of the temperature error signal generating means to the operating characteristics of the gas turbine and its associated control system.

The matched response temperature error signal generation is supported by means for generating a temperature limit signal which is clamped to a fixed, predetermined percentage of the fuel scheduling signal. This clamped signal is selectively utilized as the temperature limit signal in place of the matched response temperature error signal whenever it is less than the latter.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 shows an isometric view of an operator's console incorporating both the primary control and local maintenance controller panels;

FIG. 2 is a block diagram illustrating the interface and cabling connections between the primary control system and the local maintenance controller, as well as the constituent elements of the latter;

FIG. 3 shows a top view of the local maintenance controller operator's panel;

FIGS. 4A-C illustrative a functional diagram of the elements of the local maintenance controller shown in FIG. 2, showing the analog control portion thereof in greater detail;

FIGS. 5A-L illustrate a schematic and functional diagram of one embodiment of a dual fuel analog control system of the local maintenance controller shown in FIG. 2;

FIGS. 6A-P depict the sequencing arrangement employed in the local maintenance controller;

FIGS. 7A-B depict the relay blocks and action thereof used for transfer initiation and monitoring in the local maintenance controller;

FIG. 8 is a functional block diagram of a portion of the primary control system showing certain control loops therein;

FIG. 9 shows a top plan view of a gas turbine power plant;

FIG. 10 shows a schematic view of a rotating rectifier exciter and a generator employed in the gas turbine power plant of FIG. 9;

FIG. 11 shows a front elevational view of an industrial gas turbine employed in the power plant of FIG. 9 and is shown with some portions thereof broken away;

FIG. 12 illustrates a block diagram of the primary digital computer implemented control system used to operate the gas turbine power plant shown in FIG. 9;

FIGS. 13-15 depict a fuel nozzle and parts thereof as employed in the gas turbine shown in FIG. 11;

FIGS. 16A-B illustrate schematically the analog circuitry associated with the computer and the primary control system, which circuitry provides control over the gas turbine fuel supply system operation and certain other plant functions; and

FIGS. 17 and 18 respectively illustrate schematic diagrams of the gas and liquid fuel supply system employed with the gas turbine shown in FIG. 11.

DESCRIPTION OF THE PREFERRED EMBODIMENT The Gas Turbine Power Plant And The Primary Control System

The gas turbine power plant and the hybrid analog/digital control system therefor is completely described in U.S. patent application Ser. No. 82,470, which is hereby incorporated herein by reference. More particularly, there is shown in FIG. 9, a gas turbine electric power plant 100 which includes an AC generator 102 driven by a combustion or gas turbine 104 through a reduction gear unit 106. In this instance, the gas turbine 104 is the W-251G simple cycle type manufactured by Westinghouse Electric Corporation. In other power plant generator applications, other industrial drive applications, and combined steam and gas cycle applications of various aspects of the invention, industrial gas turbines having larger or smaller power ratings, different cycle designs, different number of shafts or otherwise different from W-251G can be employed.

The plant 100 may be housed in an enclosure (not shown) and then placed on a foundation approximately 106 to 115 feet long dependent upon the number of optional additional plant units to be accommodated thereon. Up to three additional units may be provided. Exhaust silencers 108 and 110 coupled respectively to inlet and exhaust duct works 112 and 114 significantly reduce noise characteristically associated with turbine power plants.

Digital computer and other control systems circuitry in a cabinet 118 provides for operation of the power plant 100 when a single plant unit is selected by the user. Associated therewith is an operator's panel 120, an automatic send/receive printer 122 and a protective relay panel 124 for sensing abnormal electric power system conditions. The number of basic master and slave units 118 through 124 provided may vary according as the number of plants being monitored and controlled.

Startup or cranking power for the plant 100 is provided by a starting engine 126 such as a diesel engine. Starting engine 126 is mounted on an auxiliary bedplate and coupled to the drive shaft of the gas turbine 104 through a starting gear unit 128. A DC motor 154 operates through a turning gear 156 which is also coupled to the gas turbine shaft starting gear 128 to drive the gas turbine at turning gear speed.

A motor control center 130 is also mounted on the auxiliary bedplate and it includes motor starters and other devices to provide for operating the various auxiliary equipment items associated with the plant 100.

A plant battery 132 is disposed adjacent to one end of the auxiliary bedplate or skid. The battery provides power for emergency lighting, auxiliary motor load, and DC computer and other control power for a period following shutdown of the plant 100 due to a loss of AC power. Also included on the auxiliary skid is pressure switch and gauge cabinet 152 which contains the pressure switches, gauges, regulators and other miscellaneous elements needed for gas turbine operation.

A switchgear pad 142 is included in the plant 100 for 15 KV switchgear including the generator breaker as indicated by the reference characters 144, 146 and 148. Excitation switchgear 150 associated with the generator excitation system is also included on the switchgear pad 142.

The generator 102 and its brushless exciter 103 are schematically illustrated in greater detail in FIG. 10. Structural details as well as details of operation are considered more fully in the aforementioned copending U.S. patent application Ser. No. 82,470, Section A2, pages 21 to 24.

Briefly, a permanent magnet field member 164 is rotated to induce voltage in a pilot exciter armature 166 which is coupled to a stationary AC exciter field 168 through a voltage regulator 170. Voltage is thereby induced in an AC exciter armature 172 formed on the exciter rotating element and it is applied across diodes mounted with fuses on a diode wheel 174 to energize a rotating field element 176 of the generator 102. Generator voltage is induced in a stationary armature winding 178 which supplies current to the power system through a generator breaker when the plant 100 is synchronized and on the line. A transformer 180 supplies a feedback signal for the regulator 170 to control the excitation level of the exciter field 168.

Various monitoring devices to be hereinafter more fully described are provided which generate input data for the plant control system. Included are vibration transducers 162 and 164 resistant temperature detectors embedded in the stator winding and thermocouples installed to measure air inlet discharge temperature and bearing oil drain temperatures. In this manner alarm conditions are provided to the control system. Additional control functions are provided to adjust base adjust rheostats 171 and 177 to provide fine generator voltage control.

The gas turbine 104 in this case is the single shaft simple cycle type having a standard ambient pressure ratio of 9.0 to 1 and rated speed of 4,894 rpm and it is illustrated in greater detail in FIG. 11. Filtered inlet air enters a multistate axial flow compressor 181 through a flanged inlet manifold 183 from the inlet ductwork 112. An inlet guide vane assembly 800 includes rotatably mounted variable inlet guide vanes 802 circumferentially spaced about the compressor inlet. The vanes 802 are mechanically coupled to a pneumatically operated positioning ring 804 by a plurality of link assemblies 806. The angle 808 at which the guide vanes 802 are disposed in relation to the air stream is uniform, having been positioned in response to the synchronous uniform movement of the link assemblies 806 occasioned by angular displacement of the positioning ring 804. Rotations of the positioning ring 804 are in response to a computer generated electrical signal which is transformed into a pneumatic signal by an inlet guide vane transducer (not shown). The pneumatic signal subsequently operates an inlet guide vane actuator piston contained in the air cylinder actuator 816, which delivers a force to an actuator bracket 814 sufficient to displace the positioning ring by the desired amount.

The compressor 181 is provided with a casing 184 which is split into base and cover parts along a horizontal plane. The turbine casing structure including the compressor casing 184 provides support for a turbine rotating element including a compressor rotor 186 through bearings 188 and 189. Vibration transducers are provided for the gas turbine bearings 188 and 189.

The compressor casing 184 also supports stationary blades 190 in successive stationary blade rows along the air flow path. Further, the casing 184 operates as a pressure vessel to contain the air flow as it undergoes compression. Bleed flow is obtained under valve control from intermediate compressor stages to prevent surge during startup.

The compressor inlet air flows annularly through a total of 18 stages in the compressor 181. Blade 192 mounted on the rotor 186 by means of wheels 194 are appropriately designed from an aerodynamic and structural standpoint for the intended service. A suitable material such as 12% chrome steel is employed for the rotor blades 192. Both the compressor inlet and outlet air temperatures are measured by suitably supported thermocouples.

Pressurized compressor outlet air is directed into a combustion system 196 comprising a total of eight combustor baskets 198 conically mounted within a section 200 of the casing 184 about the longitudinal axis of the gas turbine 104. Combustor shell pressure is detected by a suitable sensor coupled to the compressor-combustor flow paths located in the pressure switch and gauge cabinet 152.

As schematically illustrated in FIG. 13, the combustor baskets 198 are cross-connected by cross-flame tubes 202 for ignition purposes. A computer sequenced ignition system 204 includes igniters 206 and 208 associated with respective groups of four combustor baskets 198. In each basket group, the combustor baskets 198 are series cross-connected and the two groups are cross-connected at one end only as indicated by the reference character 210.

Generally, the ignition system 204 includes an ignition transformer and wiring to respective spark plugs which form a part of the igniters 206 and 208. The spark plugs are mounted on retractable pistons within the igniters 206 and 208 so that the plugs can be withdrawn from the combustion zone after ignition has been executed.

A pair of ultraviolet flame detectors 212 are associated with each of the end combustor baskets in the respective basket groups in order to verify ignition and continued presence of combustion in the eight combustor baskets 198. The flame detectors 212 can for example be Edison flame detectors Model 424-10433.

In FIG. 17 there is shown a front plan view of a dual fuel nozzle mounted at the compressor end of each combustor basket 198. An oil nozzle 218 is located at the center of the dual nozzle 216 and an atomizing air nozzle 220 is located circumferentially about the oil nozzle 218. An outer gas nozzle 222 is disposed about the atomizing air nozzle 220 to complete the assembly of the fuel nozzle 216.

As indicated in the broken away side view in FIG. 15, fuel oil or other liquid fuel enters the oil nozzle 218 through a pipe 224 while atomizing air for the fuel oil enters a manifold pipe arrangement 226 through entry pipe 228 for flow through the atomizing air nozzle 220. Gaseous fuel is emitted through the nozzle 222 after flow through entry pipe 230 and a manifold pipe arrangement 232.

Generally, either liquid or gaseous or both liquid and gaseous fuel flow can be used in the turbine combustion process. Various gaseous fuels can be burned including gases ranging from blast furnace gas having low BTU content to gases with high BTU content such as natural gas, butane or propane.

With respect to liquid fuels, the fuel viscosity must be less than 100 SSU at the nozzle to assure proper atomization. Most distillates meet this requirement.

A portion of the compressor outlet air flow combines with the fuel in each combustor basket 198 to produce combustion after ignition and the balance of the compressor outlet air flow combines with the combustion products for flow through the combustor basket 198 into a multistage reaction type turbine 234. The combustor casing section 200 is coupled to a turbine casing 236 through a vertical casing joint 238. No high pressure air or oil seal is required between the compressor 181 and the turbine 234.

The turbine 234 is provided with three reaction stages through which the multiple stream combustion system outlet gas flow is directed in an annular flow pattern to transform the kinetic energy of the heated, pressurized gas into turbine rotation, i.e. to drive the compressor 181 and the generator 102. The turbine rotor is formed by a stub shaft 239 and three disc blade assemblies 240, 242 and 244 mounted on the stub shaft by through bolts. Thermocouples are supported within the disc cavities to provide cavity temperature signals for the control system.

High temperature alloy rotor blades 246 are mounted on this discs in forming the disc assemblies 240, 242 and 244. Individual blade roots are cooled by air extracted from the outlet of the compressor 181 and passed through a coolant system in the manner previously indicated. The blade roots thus serve as a heat sink for the rotating blades 246. Cooling air also flows over each of the turbine discs to provide a relatively constant low metal temperature over the unit operating load range.

In addition to acting as a pressure containment vessel for the turbine 234, the turbine casing 236 supports stationary blades 248 which form three stationary blade rows interspersed with the rotor blade rows. Gas flow is discharged from the turbine 234 substantially at atmospheric pressure through a flanged exhaust manifold 250 to the outlet ductwork 114.

The generator and gas turbine vibration transducers can be conventional velocity transducers or pickups which transmit basic vibration signals to a vibration monitor for input to the control system. A pair of conventional speed detectors are associated with a notched magnetic wheel supported at appropriate turbine-generator shaft locations. Signals generated by the speed detectors are employed in the control system in determining power plant operation.

Thermocouples are associated with the gas turbine bearing oil drains. Further, thermocouples for the blade path are supported about the inner periphery of the exhaust manifold 250 to provide a fast response indication of blade temperature for control system usage particularly during plant startup periods. Exhaust temperature detectors are disposed in the exhaust ductwork 114 primarily for the purpose of determining average exhaust temperature for control system usage during load operations of the power plant 100. Suitable high response shielded thermocouples for the gas turbine 104 are those which use compacted alumina insulation with a thin-wall high alloy swaged sheath or well supported by a separate heavy wall guide.

A fuel system 251 is provided for delivering gaseous fuel to the gas nozzles 222 under controlled fuel valve operation as schematically illustrated in FIG. 17. Gas is transmitted to a diaphragm operated pressure regulating valve 254 from the plant gas source. A pressure switch 255 provides for transfer to oil fuel at a low gas pressure limit. Pressure switches 257 and 259 provide high and low pressure limit control action on the downstream side of the valve 254. It is noted at this point in the description that IEEE switchgear device numbers are generally used herein where appropriate as incorported in American Standard C37/2-1956.

A starting valve 256 determines gas fuel flow to the nozzles 222 at turbine speeds up to approximately 10% rated flow, and for this purpose it is pneumatically positioned by an electropneumatic converter 261 in response to an electric control signal. At gas flow from 10% to 100% rated, a throttle valve 258 determines gas fuel flow to the nozzles 222 under the pneumatic positioning control of an electropneumatic converter 263 and a pneumatic pressure booster relay 265. The converter 263 also responds to an electric control signal as subsequently more fully considered.

A pneumatically operated trip valve 260 stops gas fuel flow under mechanical actuation if turbine overspeed reaches a predetermined level such as 110% rated speed. A pneumatically operated vent valve 262 allows trapped gas to be vented to the atmosphere if the trip valve 260 and an on/off pneumatically operated isolation valve 264 are both closed. The isolation valve fuel control action is initiated by an electric control signal applied through the pressure switch and gauge cabinet 152. A pressure switch 267 indicates fuel pressure at the inlet to the nozzles 222.

As schematically shown in FIG. 18, a liquid fuel supply system 266 provides for liquid fuel flow to the eight nozzles 218 from the plant source through piping and various pneumatically operated valves by means of the pumping action of a turbine shaft driven main fuel pump 268. Pump discharge pressure is sensed for control system use by a detector 269. A bypass valve 271 is pneumatically operated by an electropneumatic converter 270 and a booster relay 272 to determine liquid fuel bypass flow to a return line and thereby regulate liquid fuel discharge pressure. An electric control signal provides for pump discharge pressure control, and in particular it provides for ramp pump discharge pressure control during turbine startup. A throttle valve 272 is held at a minimum position during the ramp pressure control action on the discharge pressure regulator valve 270. A pressure switch 269 provides for DC backup pump operation on low pressure, and a pressure switch 271 indicates whether the pump 268 has pressurized intake flow.

After pressure ramping, the pneumatically operated throttle valve 272 is positioned to control liquid fuel flow to the nozzle 218 as determined by an electropneumatic converter 274 and a booster relay 276. An electric control signal determines the converter position control action for the throttle valve 272. The bypass valve 270 continues to operate to hold fuel discharge pressure constant.

As in the gas fuel system 251, a mechanically actuated and pneumatically operated overspeed trip valve 278 stops liquid fuel flow in the event of turbine overspeed. A suitable filter 280 is included in the liquid fuel flow path, and, as in the gas fuel system 251, an electrically actuated and pneumatically operated isolation valves provides on/off control of liquid fuel to a liquid manifold 283.

Eight positive displacement pumps 284 are respectively disposed in the individual fuel flow paths to the nozzles 218. The pumps 284 are mounted on a single shaft and they are driven by the oil flow from the manifold 283 to produce substantially equal nozzle fuel flows. Check valves 286 prevent back flow from the nozzles 218 and a pressure switch 288 indicates fuel pressure at the oil nozzles 218. A manifold drain valve 290 is pneumatically operated under electric signal control during turbine shutdown to drain any liquid fuel remaining in the manifold 283.

Details concerning plant performance characteristics are contained in the aforementioned, related U.S. Pat. application Ser. No. 82,470, Section A4, pages 32 to 36.

The preferred embodiment of the integrated turbine generator control system 300 (FIG. 12) employs analog digital computer circuitry to provide sequenced start-stop plant operation, monitoring and alarm functions for plant protection and accurately, reliably and efficiently performing speed/load control during plant startup, running operation and shutdown. The plant control system 300 is characterized with centralized system packaging having a single operator's panel and embracing elements disposed in the control cabinet 118, the pressure switch and gauge cabinet 152 and other elements included in the electric power plant 100 of FIG. 9. If multiple plants like the power plant 100 are to be operated, plural control cabinets may be required to provide the additional circuitry needed for the additional plant operations.

The control philosophy embodied in the control system 300 provides flexible operator/control system interfaces. Under automatic control, the power plant 100 can be operated under local operator control or it can be unattended and operated by direct wired remote or supervisory control.

In FIG. 8, a control loop arrangement 302 represented by SAMA standard function symbols characterizes the preferred general control looping embodied in the preferred control system 300 and applicable in a wide variety of other applications of the invention. Reference is made to the aforementioned, copending U.S. patent application Ser. No 82,470, Section B2, pages 39 to 51, wherein there is contained a more detailed discussion of the control loop 302.

Briefly, the control loop arrangement 302 comprises an arrangement of blocks in the preferred configuration of process control loops for use in operating the gas turbine power plant 100 or other industrial gas turbine apparatus. No delineation is made between hardware and software elements since many aspects of the control philosophy can be implemented in hard or soft form. However, it is noteworthy that various advantages are gained by hybrid software-hardware implementation of the control arrangement 302 and preferably by implementation in the hybrid form represented by the control system 300.

Generally, in the various control mode sequences to be hereinafter more fully discussed, the plant 100 is started from rest under control of loop 302, accelerated under accurate and efficient control to synchronous speed, preferably in a normal fixed time period, synchronized manually or automatically with the power system, and loaded under preferred ramp control to a preselectable constant or temperature limit controlled load level, thereby providing better power plant management.

In the combination of plural control loop functions in the arrangement 302, a low fuel demand selector block 316 is preferably employed to limit the speed reference fuel demand representation if any of three limit representations are exceeded by it during startup. These limit representations are generated respectively by a surge control 318, a blade path temperature control 320, and an exhaust temperature control 322. In this application, a load control block 324 becomes operative after synchronization with the limit blocks 318, 320 and 322. Thus, the operation of the plural control loop 302 as a function of the various limit representations varies during the various control modes of operation.

At the output of the low fuel demand selector 316, the fuel demand representation is applied to a dual fuel control 317 where the fuel demand signal is processed to produce a gas fuel demand signal for application to the gas starting and throttle valves or a liquid fuel demand signal for application to the oil throttle and pressure bypass valve or as a combination of gas and liquid fuel demand signals for application to the gas and oil valves together.

In order to start the plant 100, the control system 300, operating in control Mode 0, requires certain status information generated by the various process sensors. Once it is logically determined that the overall plant status is satisfactory, the plant startup is initiated. Plant devices are started in parallel when possible to increase plant availability for power generation purposes.

As control is transferred through the various control modes a feedforward characterization is preferably used to determine representation of fuel demand needed to satisfy speed requirements. Measured process variables including turbine speed, the controlled load variable or the plant megawatts, combustor shell pressure and turbine exhaust temperatures are employed to limit, calibrate or control the fuel demand so that apparatus design limits are not exceeded. The characterization of the feedforward speed fuel demand, a surge limit fuel demand and a temperature limit fuel demand are preferably non-linear in accordance with the nonlinear characteristics of the gas turbine to achieve more accurate, more efficient, more available and more reliable gas turbine apparatus operation. The control arrangement 302 has capability for maintaining cycle temperature, gas turbine apparatus speed, acceleration rate during startup, loading rate and compressor surge margin.

The fuel demand in the control arrangement 302 provides position control for turbine gas or liquid fuel valves. Further, the control arrangement 302 can provide for simultaneous burning of gas and liquid fuel and it can provide for automatic bumpless transfer from one fuel to the other when required.

The control arrangement 302 is implemented such that different process variables are given greater weight in determining the control function to be performed as control progresses sequentially through the modes of operation.

The control system 300 is shown in block diagram detail in FIG. 12. It includes a general purpose digital computer system comprising a central processor 304 and associated input/output interfacing equipment such as that sold by Westinghouse Electric Corporation under the trade name Prodac 50 (P50). Generally, the P50 computer system employs a 16,000 word core memory, with a word length of 14 bits and a 4.5 microsecond cycle time.

More specifically, the interfacing equipment for the computer 304 includes a contact closure input system 306 and a conventional analog input system 308. Sixty-four input/output channels each having 14 bit parallel paths into and out of the main frame are provided. Each of the employed interrupt inputs causes a separate and unique response within the computer main frame without need for additional input operations thereby allowing the processing of interrupt input signals with very little main frame duty cycle.

Process inputs are provided by the contact closure input system 306 and the analog input system 308. The contact closure input (CCI) system is coupled to the operator console panel 120 and remote operator's panel 322. Characteristic CCI's are those related to the starting engine contacts. Also, a facility exists for customer selection of devices to be coupled to the CCI system.

Characteristic inputs to the analog input system 308 are the outputs from the various plant process sensors and detectors, namely, turbine 104 sensors such as blade path and exhaust manifold thermocouples. Additional inputs are those from a combustor shell pressure sensor and the main and backup speed sensors. The speed sensor outputs are coupled to the analog input system 308 through an analog speed control 324 and an auxiliary speed limiter 326, respectively.

The computer supplies essential outputs of various description for display at the operator's console 120 or the like. They are also applied as analog inputs as indicated by reference character 330. The contact closure output system 316 transfers digital speed reference, speed/load limit and fuel transfer outputs to its external circuitry as indicated respectively by the reference characters 332, 334 and 336.

The coupling of the contact closure output system 316 with the analog speed control 324 is within the framework of the preferred software/hardware hybrid control system. Another contact closure output 338 to the analog speed control 324 provides for a minimum fuel flow into the turbine combustor system in order to prevent flameout after ignition.

An analog dual fuel control system 337 is operated by the speed control 324 to determine the position of the liquid and gas fuel valves considered in connection with FIGS. 12 and 19. A contact closure output coupling to the dual fuel control 337 provides for transfer between fuels or relative fuel settings for two fuel or single fuel operation as indicated by the reference character 336.

The contact closure output system 316 is also connected to the operator's panel 120 and to sequence the starting engine 126. A synchronizer detection circuit 342 has bus line and generator potential transformers coupled to its input and the contact closure output system 316 signal provides a visual panel indication for manual synchronization. The detection circuit 342 also supplies signals to the analog input system 308 for automatic synchronization when such synchronization is employed as considered more fully in the aforementioned Reuther and Reed copending patent applications.

Other devices operated by the contact closure outputs include the generator field breaker and the generator line breakers 132 and 137. The motor operator generator exciter field rheostat 171 and 177 and various devices in the motor control center 130 and the pressure switch and gauge cabinet 152 also function in response to contact closure outputs. The printer or teletype 310 is operated directly as a special input/output channel to the main frame 304.

The Local Maintenance Controller -- General

The local maintenance controller 501 (hereinafter the LMC), as previously noted, provides a convenient, reliable and efficient means of continuing plant operation during maintenance or failure of the primary control system. As shown in FIG. 1, the LMC operator's panel 500 is conveniently mounted above the primary control operator's panel 502 in a console 504. If the computer goes down or during LMC controlled maintenance periods, the operator only has to remove panel cover 506 to expose the LMC operator's panel 500. The LMC operator's panel is shown in greater detail in FIG. 3. The details of the operator's panel 500 are set forth in the appendix of incorporated Ser. No. 476,182 and should be referred to for panel item identification and specific information.

Because of the convenient mounting arrangement, all operator controls, meters and indicators are advantageously arrayed within the operator's view and reach. The LMC panel 500 includes separate speed and fuel demand indicators, but meters indicating megawatts, synchronous phase angle an kilovolts are not duplicated on the LMC. These meters, which are on the primary control operator's panel 502, are direct wired to the generator analog transducers and are therefore not affected by the disconnection of the computer from the overall system.

FIG. 2 illustrates the cabling interface between the primary control system and the LMC. As shown therein, all analog and contact outputs that are switched between the LMC 501 and the computer are transferred in the LMC 501 through transfer relays (not shown) mounted in transfer panel 508. All inputs to the overall control system from the plant are paralleled at the paralleling panels 510 at the point where they enter from the field. This reduces the amount of cabling required, as well as the transfer hardware, and keeps the computer cables within the computer cabinet. In addition, this procedure provides for continuous computer monitoring of all variables prior to a required transfer to LMC operation. The signals used by the LMC are shown in Table I of the referenced appendix. These consist of CCO's, CCI's and analog signals. Using the cabling scheme illustrated in FIG. 2, signals from the plant are switched between the LMC and the primary control system by means of the transfer relays. The paralleled inputs to each control system are isolated from each other by diodes.

Turbine exhaust blade thermocouple inputs to the LMC 501 are connected in parallel with those inputs to the computer. A transfer switch provides for receipt of the temperature signal, developed by these thermocouples, by the operative control system. When the plant is being operated by the LMC, the computer merely follows the thermocouple readings. When the plant is under primary control, the transfer switch action disconnects the inputs to the LMC.

Before a transfer of control to the LMC can be initiated, the "Transfer Enable" pushbutton on LMC panel 500 must be depressed. If both the "Lube Oil" and "Turning Gear" toggle switches are on and the LMC system is properly tracking, the "Transfer Enable" pushbutton lights to indicate that the LMC is ready to accept either automatic or manual transfer. The turbine must be operating on a single fuel, either oil or gas, with the generator breaker are closed for successful on-line transfer to occur. There are systems where a remote primary control panel is utilized. On such systems, an indicator light is added to the panel to show that transfer to the LMC has been made. Another light added to the remote panel provides information concerning the LMC to the operator and confirms that the LMC is tracking and enabled.

The logic required for automatic transfer of control to the LMC in the event of computer failure is contained in the relay sequencer, see FIGS. 6A-P and 7A-B. This unit comprises 43 relays and associated circuitry and is mounted on two printed circuit boards within the LMC console. The relay sequencer also embodies all of the logic required to accomplish a startup with the LMC as well as alarm and trip circuits for turbine protection. When the computer fails, assuming the LMC has been enabled as described above, a relay in the primary control system indicates to the LMC that transfer of control is necessary. During the following 1 to 2 seconds, control signals to all valves are held constant while the sequence and alarm logic is reset. The LMC then automatically takes over turbine control. Manual transfer from the primary control system, with the computer continuing to operate or disabled for maintenance purposes, is accomplished in a similar manner, starting from the "Transfer Enable" pushbutton actuation. In this latter case, however, the transfer is initiated by depressing the "LMC On" pushbutton, rather than by computer failure.

Transfer from primary to LMC control is initiated in the LMC sequencer from either detection of primary control system failure or manual selection from the operator's panel. While the primary control system is functioning, the LMC acts as a tracting system to insure minimum fuel valve position change when a transfer occurs. The LMC also continuously monitors and compares the fuel demand signal it develops and the fuel demand signal developed by the primary control system. Should a signal disparity exceed prescribed limits, the LMC will initiate a transfer prevent signal. The LMC also monitors and compares against maximum limits the blade path temperature, compressor vibration and turbine exhaust end vibration and will initiate turbine trip and shutdown from these sources.

If all permissives are satisfactory, the LMC will assume turbine speed/load control upon primary control system to LMC transfer. The transfer will be accomplished at identical fuel valve position values existing under primary control immediately prior to transfer. Hence, transfer is accomplished at existing megawatt output, blade path temperature and fuel oil pump discharge pressure.

Following transfer to the LMC, blade path temperature is limited to a peak load reference curve developed within the speed/load reference generator 512 (see FIGS. 2 and 4A-B) and oil pump discharge pressure is controlled to its setpoint as developed within the LMC. Thus, should the transfer occur above peak load, i.e. -- when the primary control has been operating the plant on system reserve, a load reduction to peak load limit will follow the transfer. Also, any disparity between primary control and LMC pressure setpoints will produce a slight change in firing rate, and consequently megawatt output, following a transfer. Thereafter, the LMC will maintain a constant, fixed megawatt output which can only be varied by the panel mounted, manually actuated, increase/decrease load pushbuttons.

Should the primary control system be taken off-line during startup, before the breaker is closed, or while the turbine is operating on a mixture of fuels, an attempt to transfer control will cause the turbine to shut down. Any attempt to change fuels during startup with the LMC will also cause shutdown, while such an attempt during LMC operation will be ignored.

In any event, the LMC is capable of automatically controlling a turbine start from ignition to synchronous speed (95%). The LMC start must be attended and manually initiated from the LMC operator's panel. However, the LMC will prevent a start if the fuel demand signal exceeds a minimum value near zero. Following ignition, the LMC automatically ramps fuel demand signal per a prescribed fuel rate timing program, subject to blade path temperature limit, terminating at approximately 95% turbine speed. Thereafter, synchronization and megawatt loading is accomplished by remote manual pushbutton operation from the LMC operator's panel.

The status input information required by the LMC analog system from the sequencer and panel contact closures are set forth in the referenced appendix as are the required analog input signals. Reference should also be had to FIGS. 2, 4A-B and 5A-L. Also set forth in the referenced appendix is a listing of the logic contact closure outputs and the analog output signals developed by the LMC analog system illustrated in FIGS. 2 and 4A-B.

The LMC analog control is shown in block diagram form in FIG. 2 and in functional form in FIGS. 4A-B. It operates in the following manner. The speed control 516, in conjunction with the speed/load reference generator 512, will compare measured speed with speed setpoints and produce a control signal proportional to the error between the compared signals. As in the primary control system, the LMC is subject to minimum and maximum limits. The minimum limit is 25% fuel flow and is set by the presence of flame and breaker closure and reset to 0% upon loss of flame by means of flip-flop control logic. The maximum limit varies from 25% to 100% fuel flow, dependent on control action of a preoverspeed cutback control loop. Under normal operating conditions, this loop provides a 100% limit. Should the turbine overspeed and approach the 110% mechanical overspeed trip limit, the maximum fuel limit decays from 100% to 25%. The purpose of this is to avoid a total turbine shutdown and to restore stable speed conditions near synchronous speed. The limit is reduced by a proportional plus derivative control action, which thusly combines both anticipatory and direct control action features.

The analog speed signal will be developed by using two sets of A and B speed cards to convert the pulses developed by the speed pick ups to linear analog speed signals. The higher of these two signals will be selected and used by the speed controller. This system will utilize the same pulse signals used by the primary control system. The systems will be parallel and both operative at the same time. The speed pulse signals will not be transferred.

A stable speed setpoint will be developed by use of an up/down counter and D to A converter, see FIGS. 4A-B. Increase or decrease commands will be developed in analog logic. The up/down counter will operate at one of four rates . Two will be used for startup, that is, to accelerate the turbine from ignition to 95% speed, one for load control and one for tracking. The two startup rates will be selected as follows:

Rate A -- Selected when the speed reference is less than 60% for GT Model 251 (72% for GT Model 501), the breaker is open, the primary control is not in service, and the system not tracking.

Rate B -- Selected when the speed reference is greater than 60%, the breaker is open, the primary control is not in service and the system not tracking. The loading rate will be selected when the breaker is closed and the primary control system not in service. The tracking rate will be selected when the primary control system is in service or flame is not present.

When the gas turbine is operating on the LMC system, the speed/load setpoint will increase at the selected rate when the increase pushbutton is depressed and a decrease request and temperature limit are not present, or when flame is on and the speed is less than 95% and the breaker is open and a decrease request and temperature limit are not present, or when flame is not present and the LMC control signal output is less than zero.

When on primary control, the speed/load setpoint will increase at the tracking rate when the LMC control signal output is less than the primary control signal output by an amount equal to the deadband of the comparator.

The speed/load setpoint will decrease at the selected rate when operating on the LMC system, if the decrease pushbutton is depressed or when flame is not present and the LMC control signal output is greater than zero. When on primary control, the speed/load setpoint will decrease at the tracking rate if the LMC control signal output is greater than the control signal output of the primary control system. When operating on the LMC system, the speed/load setpoint cannot be increased if LMC control signal output exceeds the blade path temperature limit.

The LMC analog blade path temperature control will function similarly to the primary temperature control in that a function of combustor shell pressure, P2C, will be the reference or maximum temperature setpoint for average blade path temperature. Only two curves will be used, start and peak. When operating on the LMC system, the temperature control will operate as a maximum temperature limit. If, after breaker closure, the speed reference is increased to 104%, the blade path temperature will control the gas turbine at peak load. During startup, or when the breaker is open, the temperature control will stop the speed setpoint ramp and decrease control signal output if the average blade path temperature equals or is greater than the reference.

The temperature reference will be developed by means of two function generators, each developing a curve as a function of combustor shell pressure. One curve will become the maximum temperature setpoint with the breaker open. The other value will be added to the first when the breaker is closed and the sum of the two will equal the running maximum temperature limit setpoint. This system will use the pressure signal from the existing primary control combustion shell pressure transmitter. It will be paralleled and not switched.

The average blade path temperature will be determined by averaging eight thermocouples and amplifying the average. Derivative action will be applied to this signal when the system is in operation, but will be disconnected when the primary control is in service and for a short time delay after control has been transferred to the LMC. This prevents an upset to the system at the time of transfer. This system will use the same thermocouples as the primary control, but they will be disconnected when the primary control is in service, as previously noted.

The temperature reference will be compared with the measured average temperature and an error signal generated. This error signal will have two different gains applied. One for increasing and one for decreasing temperature. The resultant signals will be limited so a narrow deadband can be incorporated in the error signal. The error signals are then applied to a proportional plus integral controller. The output of this controller will be high limited to a value corresponding to approximately 110% of the LMC control signal output. Thus, maximum full load bias will be approximately 0.5 volts, but will decrease as the control signal output decreases. Using the two separately adjustable gains in the temperature controller will permit the fuel to be decreased much faster than it will be increased and will provide increased protection and greater stability to this portion of the system.

The LMC control signal output is derived from the low selection of speed controller and temperature controller outputs. This signal is applied to the LMC fuel valve controls in the identical manner as the primary control signal output is applied to the primary control valve position analog controls. The valve controls are duplicated in both control systems, thus valve position output signals are continuously available from either.

Transfer from the primary control system to the LMC will be accomplished by energizing relays containing four contacts, one for each fuel valve demand signal. The transfer command signal will be developed in the sequencer portion of the LMC system and will not be described here. These four signals, the eight thermocouple signals and other signals as required by the sequencer will be transferred at the same time.

The LMC control signal output and the four LMC valve position demand signals are monitored and compared individually with the corresponding signals from the primary control system. Any disparity in these signal comparisons exceeding preset value will result in a transfer prevent, locking turbine control to the existing mode, either primary or LMC, until the disparity is cleared.

The referenced appendix also contains, in addition to previously noted references, the following: (a) Descriptive Bulletin 23-833; (b) transfer subsystems; (c) LMC Analog Control System -- Maintenance and Calibration Instruction; and (d) Instruction Book -- Local Maintenance Controller for Gas Turbine Systems.

Matched Blade Path Temperature Limit Signal Generation

The present invention will be described in the context of a local maintenance or backup controller of the type described in the aforereferenced U.S. patent application Ser. No. 476,182. However, it will be understood by those versed in this art, that the present invention is equally employable in a primary control system and is, therefore, not intended to be limited to the use environment described hereinafter.

Referring first to FIGS. 4A-C, it can be seen that the LMC CSO (control signal output) is ultimately developed on line 401. This signal is then conveyed to the operator's panel 500 where it is amplified and forwarded to the appropriate fuel valve amplifier in the primary control system. An increase in LMC CSO will result in increased speed, while conversely, a decrease in that signal will result in lowered speed due to an increase or decrease in fuel flow. The LMC CSO is developed in the following manner.

AND gate 402 has four inputs thereto. Once the LMC mode of operation has been selected and a turbine start is contemplated thereunder, the LMC MODE and BREAKER OPEN (circuit breaker open) inputs to gate 402 are set to a logical high. If turbine speed is less than 95% of synchronous speed, the low speed signal monitoring block 420 sets a third input to gate 402 to a logical high. Once ignition has been achieved and recognized, the FLAME input to gate 402, its fourth and last input, is also set to a logical high. Thus, the output of gate 402 is set high, causing OR gate 403 to similarly set one of three inputs to AND gate 404. The other two inputs to gate 404, which indicate respectively that a speed decrease has not been called and that a speed increase permissive has been satisfied, are assumed to be at a logical high and so, the output of gate 404 causes the digital counter 405 to be incremented upwards at a rate determined by clock 421.

As will be noted by reference to FIG. 4C, clock 421 is able to increment the up/down counter 405 at one of four rates. These are (1) a tracking rate, (2) a loading rate, (3) a speed rate A and (4) a speed rate B. It should be noted that the particular clock rate selected for ramping the speed reference signal, which appears on line 408, is determined by the rate logic AND gates 431-433. AND gate 430 is utilized in clocking counter 405 at the predetermined loading rate. It should be further noted that the tracking rate is utilized to increment the counter 405 whenever the primary control system is, in fact, in control of the turbine or whenever, under LMC control, there is an absence of flame or pre-ignition. OR gate 434 responds to either of these conditions and sets the TRACKING STATE line 435 to a logical high should either occur.

In the tracking mode or state, the LMC CSO is held equal to the speed setpoint or reference minus the actual speed as measured by appropriate sensors previously identified. Thus, if at any time the actual speed experiences a sudden jump upwards, the LMC CSO will become negative until the speed setpoint or reference signal catches up. As previously noted, such an event actually occurs at ignition due to the fixed energy input resulting from the ignition process. Thus, with the turbine rotating at 20% speed, under the influence of the starting motor package, the sudden inflow of fuel via a fixed, minimum fuel valve setting and pressure typically yields a rapid, almost instantaneous, speed increase in the order of 30 to 40% of ignition speed.

If ramping of the speed setpoint signal is not delayed at ignition, a negative LMC CSO or fuel demand signal will occur because of the sharp increase in turbine speed. Since the period in which speed setpoint catches up to the actual turbine speed, under certain ambient conditions, may now exceed the atomizing air time, flameout could occur. This will, of course, delay placement of the turbine on-line and defeat the very reasons for having a local maintenance or backup controller or a control system which is designed to place a turbine on-line as quickly as possible.

This potential problem is solved by utilization of a signal time delay means 450 which is shown in FIG. 4C. A signal, "flame instant", is received from the turbine combustors, which signal verifies that ignition has taken place. This signal is fed to AND gate 451 and a 50 second time delay block 450. After expiration of the time delay period, one input to OR gate 452 is set to a logical high, which, in turn, sets line 453 to a logical high. The other input to AND gate 451 constitutes a signal indicative of turbine speed in excess of 60% of operational speed. Since this condition does not obtain at ignition speed levels, AND gate 451 has no effect on OR gate 452 until the turbine speed has been ramped up to greater than 60%. Line 453, the "flame control" line also appears in FIG. 4A and, as previously discussed, the lack of a logical high signal thereon is determinative of the operational state of the LMC.

Delay means 450 is selected to impart a 50 second delay to the "flame instant" signal, which delay retards commencement of the speed setpoint signal by that amount. The 50 second delay period has been selected in the preferred embodiment as a compromise between the time required for the speed setpoint signal to catch up with the actual measured speed and the time period in which ambient conditions may result in flameout. Consequently, at the tracking rate, the speed setpoint has caught up to the measured speed resulting in a zero CSO and permitting speed setpoint ramping to begin.

After the speed setpoint signal has been incremented, either up or down by counter 405, it is converted from a digital to an analog signal by the D/A converter 406. It is then forwarded to summing block 407, where an additional load compensation signal is added thereto if the line breaker has been closed. The speed setpoint signal is then forwarded to the differencing plus proportional block 409 where a speed error signal is developed and multiplied by an appropriate constant. From block 409, the speed error signal is forwarded to a proportional plus rate block 410 where the error signal is "kicked" or sharply increased.

Thereafter, the error signal is forwarded to a low signal selector 411, where it or an overspeed prevent signal is selected, depending on which of the input signals is lower. From there, the selected signal, which will be assumed to be the speed error signal, is forwarded to the high signal selector block 412, where it or a minimum speed error signal is selected depending on which of the two signals is higher. After being increased by the action of proportional block 413, the speed error signal arrives at the low signal select block 414. The winning signal in select block 414 appears on line 401 and, as previously noted, is conveyed to the operator's panel 500 where it is amplified and then forwarded to the appropriate fuel valve amplifier in the primary control system.

In low signal select block 414, the speed error signal is compared to a blade path temperature limit signal, with the lowest of the two being utilized to control fuel scheduling. Under most control circumstances, the speed error signal will be selected, with the temperature limit signal being utilized to insure that any speed increases called for by the control system will not violate the permissible temperature limit for the blade path.

The blade path temperature limit signal is generated in the following manner. Temperature sensors 435 generate a signal proportional to actual blade path temperature, which signal is "kicked" up only by the combined effects of rate block 440 and low signal limiting block 441. The resultant signal, therefore, anticipates a problem with respect to the temperature limit before it occurs and thereby prevents overshoot. Assuming that the LMC mode of operation is plus 12 seconds, the anticipated temperature signal is summed in block 442 with the measured signal and forwarded to differencing block 443. In block 443, the summed temperature signal is compared to a characterized combustor shell pressure signal or temperature limit setpoint signal developed by the combined action of pressure sensor 436, characterizing blocks 437 and 438, breaker status decisional block 454 and the summing block 439.

A temperature error signal is developed in block 443 by comparing the measured and setpoint signals and the resultant signal is forwarded to function point 455. If the error signal is positive, meaning that the measured temperature is above the temperature setpoint, the high temperature proportional signal limiter 444, which is active only when the temperature error signal is greater than zero, increases the signal by a factor of 5. This increased signal is forwarded to the proportional plus integral plus high signal limiter block 446 where the increased error signal is integrated at a rate which is a function of the proportional constant set in block 444. Thus, the blade path temperature limit signal developed in block 446 will now tend to drive the measured temperature towards the temperature setpoint at a relatively rapid rate which is related to the proportional constant of block 444. This constant is selected and matched to the inertial characteristics of the gas turbine, i.e. its response to fuel cutback. It will be appreciated that the rate at which fuel can be reduced in order to lower blade path temperature is realistically limited by turbine and thermal response and that beyond a given rate of fuel reduction, there will be no increased rate of temperature reduction.

Conversely, if the temperature error signal is negative, meaning that the measured temperature is below the temperature setpoint, the low temperature proportional signal limiter 445, which is active only when the temperature error signal is less than zero, decreases the error signal by a factor of 1. This decreased signal is also forwarded to block 446 where it is integrated at a rate which is a function of the proportional constant set in block 445. Thus, the blade path temperature limit signal developed in block 446 will now tend to allow the measured temperature to approach the temperature setpoint at a relatively slow rate which is related to the proportional constant of block 445. This constant is selected and matched to the response characteristics of the gas turbine and control system, i.e. the response to fuel increase.

Thus, by appropriate selection of the proportional constants of blocks 444 and 445, the generation of the blade path temperature error signal is matched or tuned to the characteristics of the gas turbine. Such generation is thereby constrained to behave in one manner in response to a condition of increasing temperature wherein fuel is increased at a relatively slow rate and in another manner in response to a condition of decreasing temperature wherein fuel is decreased at a relatively rapid rate.

After final conditioning in block 446, the blade path temperature error signal is also compared therein to a temperature limiting signal which is clamped at a predetermined percentage of the control signal output or fuel scheduling signal and appears on line 447. If the blade path temperature error signal is not higher than the clamped limit signal then it is forwarded by block 446 to the low signal selector 414 via line 448 and serves as the temperature limit signal thereat. However, if the error signal is higher than the clamped limit signal, then the clamped signal is forwarded to block 414 to serve as the blade path temperature limit. Since the error signal will most often be used as the temperature limit signal, particularly after ignition, it is fair to equate the error signal and the limit signal in describing operation of the present invention.

The clamped, temperature limit signal which appears on line 447 is generated in the following manner. The inputs to decision block 460 are connected respectively to the primary control fuel scheduling signal (P50 CSO) and the backup control fuel scheduling signal (LMC CSO or line 401). If the plant is being operated by the primary control system or is capable of being so operated (P50 MODE), decision block 460 forwards the fuel scheduling signal thereof to decision block 461. Conversely, if the plant is being or is to be operated by the backup control system (LMC MODE), decision block 460 forwards the fuel scheduling signal thereof to decision block 461.

At decision block 461, the forwarded signal is passed to the proportional multiplying block 462, where it is multiplied by a fixed, predetermined percentage, in the preferred embodiment by 110%, if the backup control system is not in its tracking mode. As will be recalled, the backup control system will ordinarily be in its tracking mode whenever the primary control system is operating the plant prior to speed setpoint ramping. If speed setpoint ramping in the backup control is not occurring, i.e. before ignition plus the delay, then the value of constant block 463, which is zero percent is forwarded to block 462.

Summing block 465 adds the signal received from multiplying block 462 to the bias signal generated in constant block 464, in the preferred embodiment a 2% portion of the fuel scheduling signal. The summed result, which appears on line 447, is therefore clamped to either 112% of the fuel scheduling signal (CSO) or to 2% thereof, depending upon the mode of control operation. Thus, after speed setpoint ramping with backup control or when the plant is operated on primary control, the clamped signal is held at 112% of the fuel scheduling signal which permits the speed error signal to dominate fuel scheduling. In its alternative state, prior to speed setpoint ramping under the aegis of the backup control, the clamped signal is held at only 2% of the fuel scheduling signal which insures that speed setpoint ramping, when initiated, will be able to increase turbine speed since a negative or very small initial fuel scheduling signal would otherwise control via the action of signal selector block 414.

Once speed ramping has occurred or begun, the clamping action of the temperature limit signal on line 447 holds the maximum temperature limit forwarded to selector block 414 at 110% of the fuel scheduling signal or CSO. This allows the speed error signal to ramp up turbine speed without bumping into the temperature limit before it should.

While the preferred embodiment has been specifically described in hardware form in a particular control environment, it will be appreciated that alternative embodiments thereof and equivalent modifications therein are possible and within the scope of the present invention. Consequently, the present invention is not intended to be limited to the precise embodiment described and shown herein, except as limited by any pertinent prior art. 

We claim:
 1. For a gas turbine power plant having a primary control system which develops a control signal output utilized to regulate a turbine fuel flow control means, backup control apparatus comprising:a. input means for receiving representations of information concerning predetermined plant operating parameters; b. speed control means, including means for generating a turbine speed setpoint signal, operably coupled to said input means for developing a speed error signal for used in adjusting fuel flow; c. temperature control means, including means for generating a blade path temperature error signal which changes at a first rate under a first condition when the measured temperature is above the setpoint and at a second rate under a second condition when the measured temperature is below the setpoint, operably coupled to said input means for developing a temperature limit signal for use in adjusting fuel flow; d. signal selector means, operably coupled between said speed control means, said temperature control means and the plant, for selecting in accordance with a predetermined criteria said speed error signal or said temperature limit signal for use in adjusting fuel flow; and e. means for applying the primary control signal output or the backup control output from said signal selector means to the fuel flow control means.
 2. The apparatus according to claim 1 wherein said means for generating a temperature error signal comprises:a. means for generating a preliminary temperature error signal; b. first circuit means, responsive to said preliminary temperature error signal and operable only under said first condition, to change said preliminary temperature error signal at a first and relatively fast rate; and c. second circuit means, responsive to said preliminary temperature error signal and operable only under said second condition, to change said preliminary temperature error signal at a second and relatively slow rate.
 3. The apparatus according to claim 2 wherein said first and second circuit means comprise:a. a first section having an adjustable proportional multiplier; b. a second section having signal input selectivity; and c. a third section having integrating capability.
 4. The apparatus according to claim 2 which further comprises.a. means, coupled to the output of said signal selector means and to said input means, for generating a temperature limit signal which is clamped to a first predetermined percentage of the signal selected by said signal selector means for a third predefined plant operating condition and to a second predetermined percentage of the primary control signal output for a fourth predefined plant operating condition; and b. high limiting signal selector means, coupled between the outputs of said temperature control means and said means for generating said clamped signal and the input of said signal selector means, for selecting either of said changed preliminary temperature error signals as said temperature limiting signal whenever they are lower in value than said clamped signal and for selecting said clamped signal as said temperature limiting signal whenever it is higher than said changed preliminary temperature error signals.
 5. The apparatus according to claim 2 wherein.a. said first temperature error change rate is substantially matched to the rate at which the turbine thermal response allows the gas temperature to drop on fuel decreases; and b. said second temperature error change rate is substantially matched to the rate at which the turbine thermal response allows the gas temperature to rise on fuel increases.
 6. Apparatus for controlling fuel flow to a turbine including:a. input means for receiving representations of information concerning predetermined turbine operating parameters; b. speed control means, including means for generating a turbine speed setpoint, operably related to said input means for developing a speed error for use in adjusting fuel flow; c. temperature control means, including means for generating a blade path temperature error which changes at a first rate under a first condition when the measured temperature is above the setpoint and at a second rate under a second condition when the measured temperature is below the setpoint, operably related to said input means, for developing a temperature limit for use in adjusting fuel flow; and d. selector means, operably related to said speed control means, said temperature control means and the turbine, for selecting in accordance with a predetermined criteria said speed error or said temperature limit for use in adjusting fuel flow.
 7. The apparatus according to claim 6 wherein said means for generating a temperature error comprises;a. means for generating a preliminary temperature error; b. first means, responsive to said preliminary temperature error and operable only under said first condition, for changing said preliminary temperature error at a first and relatively fast rate; and c. second means, responsive to said preliminary temperature error and operable only under said second condition, for changing said preliminary temperature error at a second and relatively slow rate.
 8. The apparatus according to claim 7 wherein said first and second means comprise:a. a first section having an adjustable proportional multiplier; b. a second section having signal input selectivity; and c. a third section having integrating capability.
 9. The apparatus according to claim 7 which further comprises:a. means, related to the output of said selector means and to said input means, for generating a temperature limit which is clamped to a first predetermined percentage of the selection by said selector means for a third predefined turbine operating condition and to a second predetermined percentage thereof for a fourth predefined turbine operating condition; and b. high limiting selector means, related between the outputs of said temperature control means and said means for generating said clamped temperature limit and the input of said selector means, for selecting either of said changed preliminary temperature errors as said temperature whenever they are lower in value than said clamped temperature limit and for selecting said clamped temperature limit as said limit whenever it is higher than said changed preliminary temperature errors.
 10. The apparatus according to claim 7 wherein:a. said first temperature error change rate is substantially matched to the rate at which the turbine thermal response allows the gas temperature to drop on fuel decreases; and b. said second temperature error change rate is substantially matched to the rate at which the turbine thermal response allows the gas temperature to rise on fuel increases. 